WO2022269174A1 - Method for manufacturing a composite blade for a turbine engine, the blade comprising a reinforcing shield for balancing the blade - Google Patents

Method for manufacturing a composite blade for a turbine engine, the blade comprising a reinforcing shield for balancing the blade Download PDF

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Publication number
WO2022269174A1
WO2022269174A1 PCT/FR2022/051176 FR2022051176W WO2022269174A1 WO 2022269174 A1 WO2022269174 A1 WO 2022269174A1 FR 2022051176 W FR2022051176 W FR 2022051176W WO 2022269174 A1 WO2022269174 A1 WO 2022269174A1
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WO
WIPO (PCT)
Prior art keywords
blade
shield
axis
edge
surplus
Prior art date
Application number
PCT/FR2022/051176
Other languages
French (fr)
Inventor
Maxime Mathieu MOUROT
Lucas Antoine Christophe LAUWICK
Julien TREBAOL
Original Assignee
Safran Aircraft Engines
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Safran Aircraft Engines filed Critical Safran Aircraft Engines
Priority to EP22744251.4A priority Critical patent/EP4359649A1/en
Priority to CN202280049936.6A priority patent/CN117716114A/en
Publication of WO2022269174A1 publication Critical patent/WO2022269174A1/en

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/027—Arrangements for balancing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/286—Particular treatment of blades, e.g. to increase durability or resistance against corrosion or erosion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/324—Blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/10—Manufacture by removing material
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/303—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the leading edge of a rotor blade

Definitions

  • the present invention relates to a method for manufacturing a blade made of composite material for a turbomachine, in particular an aircraft, as well as a method for assembling a turbomachine module, such as a fan module.
  • the technical background includes in particular the documents CA-A1-
  • An aircraft turbine engine comprises one or more propellers which may be ducted or unducted.
  • the present invention applies in particular to the blades of a fan, that is to say to the blades of a ducted propeller, but also to other types of propellers, such as the unducted propellers of turboprop engines for example.
  • a turbomachine propeller is crossed by a flow of air and its blades can suffer damage by wear or impact, for example of the FOD type (acronym for English Flying Object Damage) caused by the impact of a bird for example on the blades.
  • FOD type acronym for English Flying Object Damage
  • the present invention relates to the manufacture of a blade made of a composite material, for example with an organic matrix (CMO), of which at least one edge is reinforced by a reinforcement shield.
  • CMO organic matrix
  • a composite blade is formed from a woven preform embedded in a polymer matrix (of the epoxy type for example).
  • the preform is obtained by three-dimensional weaving of fibers, generally carbon.
  • 3,046,557 comprises two lateral wings extending respectively over a lower surface and an upper surface of the blade, and a nose connecting the two wings.
  • These composite blades can equip a turbomachine module such as a fan module.
  • a fan module includes a rotor disk on which the blades are mounted. This type of module must be balanced to remove or reduce any unbalance. Balancing is conventionally carried out by attaching and fixing weights on the module, these weights having predetermined masses and being positioned precisely to compensate for the aforementioned unbalance.
  • the flyweights are attached to the disc or the fan cone, which allows the radial moment weight of the complete module to be adjusted. There is currently no workaround to adjust this setting on individual blades.
  • the moment of a force with respect to a given point is a vectorial physical quantity reflecting the ability of this force to rotate a mechanical system around this point.
  • the force depends mainly on the mass of a blade.
  • the moment of force considered for balancing therefore depends on the weight and is called “moment weight”.
  • the radial moment weight of the fan blades is a critical parameter on the problems of the service life of the fan disc and the fan blades or the balancing of the complete set of blades. There is therefore an interest in reducing the dispersion of production on this parameter. In order to improve the radial moment weight capability of the blade, it would be useful to be able to vary the mass of each of the blades by approximately +/-15g in a particular embodiment.
  • the present invention proposes a simple, effective and economical solution to the need mentioned above.
  • the present invention proposes a method for manufacturing a composite material blade for a turbine engine, in particular an aircraft, comprising the steps of: a) and b) preparation of a blade based on fibers embedded in a resin, the blade comprising an extrados and an intrados extending between a leading edge and a trailing edge, c) fixing a shield of reinforcement on one edge of the blade, this shield having a generally elongated shape along an axis of elongation of the blade, characterized in that the shield fixed in step c) comprises at least one oversizing so as to be able to adjusting the moment weight of the blade along said axis as a function of the position of the shield on the edge along this axis, and in that the method comprises a following step d) of removing a surplus from the shield.
  • the invention thus proposes to adjust the moment weight, in particular the radial moment, of a blade, before it is mounted in a module, for example a fan.
  • the blades can thus be balanced before assembly of the module. This makes it possible to eliminate the balancing of the complete module and therefore to avoid using balancing weights, which is particularly advantageous.
  • the blades of the vanes have complex profiles, generally twisted and cambered.
  • the shields have shapes configured to adopt those of the blades and can each have a section that changes in the longitudinal direction. It is therefore understood that the moment weight of the blade is affected by the positioning of the shield on the edge, along the aforementioned axis.
  • the shield generally has a length which is a function, and in particular which is equal, to the length or longitudinal dimension of the edge on which the shield is mounted.
  • the oversizing of the shield, in particular in length allows different longitudinal positioning of the shield on the edge which will thus always be covered by the shield regardless of the position of the shield, as will be explained in more detail below.
  • the method according to the invention may comprise one or more of the following characteristics and/or steps, taken separately from each other or in combination with each other:
  • steps a) and b) respectively comprise: a) weaving fibers in three dimensions so as to obtain a fibrous preform, and b) assembly of the preform in a mold and injection of resin into this mold, so as to obtain a blade comprising an extrados and an intrados extending between a leading edge and a trailing edge,
  • steps a) and b) comprise the stacking of sheets or fabrics of fibers, which are previously or subsequently impregnated with a resin;
  • the surplus is located at a lower or radially inner end of the blade, or at an upper or radially outer end of the blade;
  • the method comprises a prior step o) of studying the impact of the position of the shield on the edge of the blade, along said axis, on the moment weight of the blade along this axis;
  • the present invention also relates to a method for assembling a turbine engine module, such as a fan module, comprising a step of e) mounting several blades on a rotor disk, each of the blades being manufactured by a method such as described above.
  • the assembly comprising the rotor disc and the blades forms a wheel.
  • the method does not include a step for balancing the module, and in particular the wheel, after mounting the blades on the disc.
  • Figure 1 is a schematic perspective view of a turbomachine propeller blade, and in particular a turbomachine fan,
  • Figure 2 is a schematic cross-sectional view of a shield of a blade such as that shown in Figure 1,
  • FIG.3 Figure 3 is a very schematic view of a fan module of an aircraft turbine engine
  • Figure 4 is a flowchart showing the steps of a method of assembling a turbomachine module, according to the technique prior to the invention
  • FIG.5 Figure 5 is a flowchart showing the steps of a method of assembling a turbomachine module, according to the invention.
  • Figures 6a-6d Figures 6a to 6d are very schematic views of a composite blade, during steps of a first embodiment of a method according to the invention for Figures 6a and 6b , and during steps of a second embodiment of a method according to the invention for FIGS. 6c and 6d.
  • FIG. 1 shows a blade 10 of a propeller and in particular of a fan of an aircraft turbomachine.
  • This blade 10 comprises a blade 12 made of organic matrix composite and a metal shield 14 bonded to a leading edge.
  • the blade 12 further comprises a trailing edge 16, opposite the leading edge, and an underside and an upper surface extending between the leading and trailing edges of the blade.
  • the blade has an axis of elongation denoted A which is a radial axis with respect to the longitudinal axis B of the turbomachine in which this blade is mounted (figure 3).
  • a longitudinal end of the blade 12 is free and the opposite longitudinal end is connected to a foot 18 for fixing the blade to a rotor of the turbomachine.
  • the shield 14 comprises two side wings 14a and 14b extending respectively over the upper surface and the lower surface of the blade 12, and a nose 14c connecting the two wings 14a and 14b.
  • the wings 14a, 14b define between them a cavity for receiving the leading edge of the blade 12, as well as glue for securing the shield to the blade.
  • the blade 10 can be manufactured by a method comprising the steps of: a) weaving fibers in three dimensions so as to obtain a fibrous preform, b) mounting the preform in a mold and injecting resin into this mold, so to obtain a blade 12 comprising an upper surface and a lower surface extending between a leading edge and a trailing edge, and c) fixing the shield 14 on the edge of the blade.
  • the blade 10 could be manufactured by stacking layers or fabrics of fibers, which are previously or subsequently impregnated with a resin.
  • the composite material of the blade comprises fibers embedded in a resin.
  • the blades 10 can be mounted on a rotor disk 22 to form a rotor wheel or a fan rotor, as can be seen in FIG. 3.
  • the rotor disk 22 comprises vanes 10 at its periphery and can be attached to a cone 24.
  • the flowchart in Figure 4 illustrates steps for assembling a fan module, according to the prior art.
  • this process comprises three steps, namely: a) the manufacture of the blades as mentioned above with the fixing of a shield, for example by gluing, on the edge of a blade, b) the assembly of the blades on the rotor disc, then finally i) the balancing of the module by evaluating its unbalance and correcting it by weights of predetermined weights, reported and fixed in precise places of the module (for example on the cone 24) .
  • FIG. 5 illustrates steps for assembling a module, for example a fan, according to the invention.
  • the last step i) of the process of FIG. 4 is eliminated since there is normally no longer any need to balance the module after mounting the blades on the disc. This is made possible thanks to the individual balancing of each blade, by adjusting their radial moment weight, i.e. their moment weight in relation to the radial axis with respect to the blade or module rotation axis.
  • the method of FIG. 5 comprises, in addition to the aforementioned steps a) and b), the steps of: c) and d), bonding the shield to the edge of the blade, this shield being positioned on the edge of the blade and dimensioned according to the radial moment weight of the blade, this step being repeated for each of the blades of the module, e) and assembly of the blades on the rotor disk.
  • the shield fixed in step c) comprises at least one oversizing (L2-L1) so as to be able to adjust the radial moment weight of the blade as a function of the longitudinal position of the shield on the edge. This oversizing is quantified as a function of the balancing to be carried out and may for example have an equivalent mass of 15g.
  • This oversizing (L2-L1) is preferably made along the longitudinal axis A or radial of the blade and is therefore an overlength, as shown in the drawings.
  • An overlength representing a mass of 15g can for example represent an overlength of 1.5cm along the axis A in a particular embodiment.
  • the excess length is quantified so that it allows sufficient movement of the shield on the blade to adjust the radial moment weight of the blade, and so that, for each of these positions, the leading edge of the blade blade is covered and protected by the shield. It is therefore understood that this excess length will be quantified according to the maximum possible displacement of the shield on the edge, to adjust the radial moment weight of the blade.
  • the radial moment weight of the blade has a minimum value.
  • the radial moment weight of the blade has a maximum value.
  • Step d) which follows step c) of positioning and gluing the shield 14 consists in removing the surplus, here longitudinal, of the shield which must not in general exceed the edge of the blade 12.
  • the excess S1 located at the radially outer end of the blade is eliminated.
  • the surplus S1 located at the end radially internal vane is removed. This removal can be achieved by machining.
  • the invention thus proposes to adjust the radial moment weight of the blades before assembling a turbomachine module, which therefore does not necessarily require proper balancing.

Abstract

A method for manufacturing a blade (10) made of a composite material for a turbine engine, in particular a turbine engine of an aircraft, wherein a reinforcing shield (14) is attached to one edge of an airfoil, said shield having a generally elongated shape along an elongation axis (A) of the airfoil. The shield (14) comprises at least one excess dimension (L2-L1) so as to be able to adjust the moment weight of the blade along the axis (A) according to the position of the shield on the edge of said axis, and the method comprises a step for removing a surplus portion (SI, S2) of the shield so as to balance the blade.

Description

DESCRIPTION DESCRIPTION
TITRE : TITLE :
PROCEDE DE FABRICATION D'UNE AUBE COMPOSITE DE TURBOMACHINE, L'AUBE COMPRENANT UN BOUCLIER DE RENFORT PERMETTANT UN ÉQUILIBRAGE METHOD FOR MANUFACTURING A COMPOSITE TURBOMACHINE BLADE, THE BLADE COMPRISING A REINFORCING SHIELD FOR BALANCING
Domaine technique de l'invention Technical field of the invention
La présente invention concerne un procédé de fabrication d’une aube en matériau composite pour une turbomachine, en particulier d’aéronef, ainsi qu’un procédé d’assemblage d’un module de turbomachine, tel qu’un module de soufflante. The present invention relates to a method for manufacturing a blade made of composite material for a turbomachine, in particular an aircraft, as well as a method for assembling a turbomachine module, such as a fan module.
Arrière-plan technique Technical background
L’arrière-plan technique comprend notamment les documents CA-A1-The technical background includes in particular the documents CA-A1-
2 999 360, CA-A1-3 009 226 et EP-A1-2 037 082. 2,999,360, CA-A1-3,009,226 and EP-A1-2,037,082.
Une turbomachine d’aéronef comporte une ou plusieurs hélice(s) qui peuvent être carénée(s) ou non carénée(s). La présente invention s’applique notamment aux aubes d’une soufflante, c'est-à-dire aux aubes d’une hélice carénée mais aussi à d’autres types d’hélices, telles que les hélices non carénées des turbopropulseurs par exemple. An aircraft turbine engine comprises one or more propellers which may be ducted or unducted. The present invention applies in particular to the blades of a fan, that is to say to the blades of a ducted propeller, but also to other types of propellers, such as the unducted propellers of turboprop engines for example.
Une hélice de turbomachine est traversée par un flux d’air et ses aubes peuvent subir des dommages par usure ou impact, par exemple du type FOD (acronyme de l’anglais Flying Object Damage) provoqué par l’impact d’un oiseau par exemple sur les aubes. A turbomachine propeller is crossed by a flow of air and its blades can suffer damage by wear or impact, for example of the FOD type (acronym for English Flying Object Damage) caused by the impact of a bird for example on the blades.
La présente invention concerne la fabrication d’une aube en matériau composite, par exemple à matrice organique (CMO), dont au moins un bord est renforcé par un bouclier de renfort. The present invention relates to the manufacture of a blade made of a composite material, for example with an organic matrix (CMO), of which at least one edge is reinforced by a reinforcement shield.
Une aube composite est formée à partir d’une préforme tissée noyée dans une matrice polymérique (du type époxy par exemple). La préforme est obtenue par tissage en trois dimensions de fibres, en général de carbone. A composite blade is formed from a woven preform embedded in a polymer matrix (of the epoxy type for example). The preform is obtained by three-dimensional weaving of fibers, generally carbon.
Il est connu de renforcer le bord d’attaque de cette aube par un bouclier métallique rapporté. Le bouclier, tel que décrit dans la demande FR-A1-It is known to reinforce the leading edge of this blade with an added metal shield. The shield, as described in application FR-A1-
3 046 557, comporte deux ailes latérales s’étendant respectivement sur un intrados et un extrados de la pale, et un nez reliant les deux ailes. Ces aubes composites peuvent équiper un module de turbomachine tel qu’un module de soufflante. Un module de soufflante comprend un disque de rotor sur lequel sont montées les aubes. Ce type de module doit être équilibré pour supprimer ou diminuer tout balourd. L’équilibrage est classiquement réalisé en rapportant et fixant des masselottes sur le module, ces masselottes ayant des masses prédéterminées et étant positionnées précisément pour compenser le balourd précité. 3,046,557, comprises two lateral wings extending respectively over a lower surface and an upper surface of the blade, and a nose connecting the two wings. These composite blades can equip a turbomachine module such as a fan module. A fan module includes a rotor disk on which the blades are mounted. This type of module must be balanced to remove or reduce any unbalance. Balancing is conventionally carried out by attaching and fixing weights on the module, these weights having predetermined masses and being positioned precisely to compensate for the aforementioned unbalance.
Les masselottes sont fixées sur le disque ou le cône de soufflante, ce qui permet d’ajuster le poids moment radial du module complet. Il n’existe actuellement pas de solution pour ajuster ce paramètre sur les aubes individuelles. The flyweights are attached to the disc or the fan cone, which allows the radial moment weight of the complete module to be adjusted. There is currently no workaround to adjust this setting on individual blades.
Le moment d’une force par rapport à un point donné est une grandeur physique vectorielle traduisant l’aptitude de cette force à faire tourner un système mécanique autour de ce point. Dans le contexte de l’invention, la force dépend principalement de la masse d’une aube. Le moment de la force considéré pour l’équilibrage dépend donc du poids et est appelé « poids moment ». La projection de ce moment sur l’axe longitudinal de l’aube qui est en général un axe radial (par rapport à l’axe de rotation de la souffante et de l’aube), s’appelle « poids moment radial ». C’est une grandeur scalaire algébrique exprimée dans la même unité que le poids moment. The moment of a force with respect to a given point is a vectorial physical quantity reflecting the ability of this force to rotate a mechanical system around this point. In the context of the invention, the force depends mainly on the mass of a blade. The moment of force considered for balancing therefore depends on the weight and is called “moment weight”. The projection of this moment on the longitudinal axis of the blade, which is generally a radial axis (relative to the axis of rotation of the fan and the blade), is called "radial moment weight". It is an algebraic scalar quantity expressed in the same unit as the weight moment.
Le poids moment radial des aubes de soufflante est un paramètre critique sur les problématiques de durée de vie du disque de soufflante et des aubes de soufflante ou d’équilibrage du jeu complet d’aubes. Il y a donc un intérêt à diminuer la dispersion de la production sur ce paramètre. Afin d’améliorer la capabilité en poids moment radial de l’aube, il serait utile de pouvoir faire varier la masse de chacune des aubes d’environ +/-15g dans un cas particulier de réalisation. The radial moment weight of the fan blades is a critical parameter on the problems of the service life of the fan disc and the fan blades or the balancing of the complete set of blades. There is therefore an interest in reducing the dispersion of production on this parameter. In order to improve the radial moment weight capability of the blade, it would be useful to be able to vary the mass of each of the blades by approximately +/-15g in a particular embodiment.
La présente invention propose une solution simple, efficace et économique au besoin évoqué ci-dessus. The present invention proposes a simple, effective and economical solution to the need mentioned above.
Résumé de l'invention Summary of the invention
La présente invention propose un procédé de fabrication d’une aube en matériau composite pour une turbomachine, en particulier d’aéronef, comprenant les étapes de : a) et b) préparation d’une pale à base de fibres noyées dans une résine, la pale comportant un extrados et un intrados s’étendant entre un bord d’attaque et un bord de fuite, c) fixation d’un bouclier de renfort sur un bord de la pale, ce bouclier ayant une forme générale allongée le long d’un axe d’allongement de la pale, caractérisé en ce que le bouclier fixé à l’étape c) comprend au moins un surdimensionnement de façon à pouvoir ajuster le poids moment de l’aube le long dudit axe en fonction de la position du bouclier sur le bord le long de cet axe, et en ce que le procédé comprend une étape suivante d) de suppression d’un surplus du bouclier. The present invention proposes a method for manufacturing a composite material blade for a turbine engine, in particular an aircraft, comprising the steps of: a) and b) preparation of a blade based on fibers embedded in a resin, the blade comprising an extrados and an intrados extending between a leading edge and a trailing edge, c) fixing a shield of reinforcement on one edge of the blade, this shield having a generally elongated shape along an axis of elongation of the blade, characterized in that the shield fixed in step c) comprises at least one oversizing so as to be able to adjusting the moment weight of the blade along said axis as a function of the position of the shield on the edge along this axis, and in that the method comprises a following step d) of removing a surplus from the shield.
L’invention propose ainsi d’ajuster le poids moment en particulier radial d’une aube, avant son montage dans un module par exemple de soufflante. Les aubes peuvent ainsi être équilibrées avant l’assemblage du module. Ceci permet de supprimer l’équilibrage du module complet et donc d’éviter d’utiliser des masselottes d’équilibrage, ce qui est particulièrement avantageux. The invention thus proposes to adjust the moment weight, in particular the radial moment, of a blade, before it is mounted in a module, for example a fan. The blades can thus be balanced before assembly of the module. This makes it possible to eliminate the balancing of the complete module and therefore to avoid using balancing weights, which is particularly advantageous.
En général, les pales des aubes ont des profils complexes, en général vrillées et cambrées. Les boucliers ont des formes configurées pour adopter celles des pales et peuvent avoir chacune une section évolutive en direction longitudinale. On comprend donc que le poids moment de l’aube est affecté par le positionnement du bouclier sur le bord, le long de l’axe précité. In general, the blades of the vanes have complex profiles, generally twisted and cambered. The shields have shapes configured to adopt those of the blades and can each have a section that changes in the longitudinal direction. It is therefore understood that the moment weight of the blade is affected by the positioning of the shield on the edge, along the aforementioned axis.
Le bouclier a en général une longueur qui est fonction, et en particulier qui est égale, à la longueur ou dimension longitudinale du bord sur lequel le bouclier est monté. Le surdimensionnement du bouclier, en particulier en longueur, autorise des positionnements longitudinaux différents du bouclier sur le bord qui sera ainsi toujours recouvert par le bouclier quelle que soit la position du bouclier, comme cela sera expliqué plus en détail dans ce qui suit. The shield generally has a length which is a function, and in particular which is equal, to the length or longitudinal dimension of the edge on which the shield is mounted. The oversizing of the shield, in particular in length, allows different longitudinal positioning of the shield on the edge which will thus always be covered by the shield regardless of the position of the shield, as will be explained in more detail below.
Le procédé selon l’invention peut comprendre une ou plusieurs des caractéristiques et/ou étapes suivantes, prises isolément les unes des autres ou en combinaison les unes avec les autres : The method according to the invention may comprise one or more of the following characteristics and/or steps, taken separately from each other or in combination with each other:
- les étapes a) et b) comprennent respectivement le : a) tissage de fibres en trois dimensions de façon à obtenir une préforme fibreuse, et le b) montage de la préforme dans un moule et injection de résine dans ce moule, de façon à obtenir une pale comportant un extrados et un intrados s’étendant entre un bord d’attaque et un bord de fuite, - steps a) and b) respectively comprise: a) weaving fibers in three dimensions so as to obtain a fibrous preform, and b) assembly of the preform in a mold and injection of resin into this mold, so as to obtain a blade comprising an extrados and an intrados extending between a leading edge and a trailing edge,
- les étapes a) et b) comprennent l’empilement de nappes ou tissus de fibres, qui sont préalablement ou ensuite imprégnés avec une résine ; - steps a) and b) comprise the stacking of sheets or fabrics of fibers, which are previously or subsequently impregnated with a resin;
- ledit surdimensionnement est une surlongueur du bouclier ; - Said oversizing is an overlength of the shield;
- ledit surplus est un surplus longitudinal du bouclier ; - Said surplus is a longitudinal surplus of the shield;
- le surplus est situé à une extrémité inférieure ou radialement interne de la pale, ou à une extrémité supérieure ou radialement externe de la pale ; - the surplus is located at a lower or radially inner end of the blade, or at an upper or radially outer end of the blade;
- le procédé comprend une étape o) préalable d’étude de l’impact de la position du bouclier sur le bord de la pale, le long dudit axe, sur le poids moment de l’aube le long de cet axe ; - the method comprises a prior step o) of studying the impact of the position of the shield on the edge of the blade, along said axis, on the moment weight of the blade along this axis;
- ledit surplus est supprimé par usinage du bouclier. - Said surplus is removed by machining the shield.
La présente invention concerne également un procédé d’assemblage d’un module de turbomachine, tel qu’un module de soufflante, comprenant une étape de e) montage de plusieurs aubes sur un disque de rotor, chacune des aubes étant fabriquée par un procédé tel que décrit ci-dessus. L’ensemble comprenant le disque de rotor et les aubes forme une roue. Avantageusement, le procédé est dépourvu d’étape d’équilibrage du module, et en particulier de la roue, postérieurement au montage des aubes sur le disque. The present invention also relates to a method for assembling a turbine engine module, such as a fan module, comprising a step of e) mounting several blades on a rotor disk, each of the blades being manufactured by a method such as described above. The assembly comprising the rotor disc and the blades forms a wheel. Advantageously, the method does not include a step for balancing the module, and in particular the wheel, after mounting the blades on the disc.
Brève description des figures Brief description of figures
D'autres caractéristiques et avantages de l'invention apparaîtront au cours de la lecture de la description détaillée qui va suivre pour la compréhension de laquelle on se reportera aux dessins annexés dans lesquels : Other characteristics and advantages of the invention will appear during the reading of the detailed description which will follow for the understanding of which reference will be made to the appended drawings in which:
[Fig.1] La figure 1 est une vue schématique en perspective d’une aube d’hélice de turbomachine, et en particulier de soufflante de turbomachine, [Fig.1] Figure 1 is a schematic perspective view of a turbomachine propeller blade, and in particular a turbomachine fan,
[Fig.2] La figure 2 est une vue schématique en coupe transversale d’un bouclier d’une aube telle que celle représentée à la figure 1 , [Fig.2] Figure 2 is a schematic cross-sectional view of a shield of a blade such as that shown in Figure 1,
[Fig.3] La figure 3 est une vue très schématique d’un module de soufflante d’une turbomachine d’aéronef, [Fig.4] La figure 4 est un organigramme montrant des étapes d’un procédé d’assemblage d’un module de turbomachine, selon la technique antérieure à l’invention ; [Fig.3] Figure 3 is a very schematic view of a fan module of an aircraft turbine engine, [Fig.4] Figure 4 is a flowchart showing the steps of a method of assembling a turbomachine module, according to the technique prior to the invention;
[Fig.5] La figure 5 est un organigramme montrant des étapes d’un procédé d’assemblage d’un module de turbomachine, selon l’invention ; et [Fig.6a-6d] Les figures 6a à 6d sont des vues très schématiques d’une aube composite, au cours d’étapes d’un premier mode de réalisation d’un procédé selon l’invention pour les figures 6a et 6b, et au cours d’étapes d’un second mode de réalisation d’un procédé selon l’invention pour les figures 6c et 6d. Description détaillée de l'invention [Fig.5] Figure 5 is a flowchart showing the steps of a method of assembling a turbomachine module, according to the invention; and [Fig.6a-6d] Figures 6a to 6d are very schematic views of a composite blade, during steps of a first embodiment of a method according to the invention for Figures 6a and 6b , and during steps of a second embodiment of a method according to the invention for FIGS. 6c and 6d. Detailed description of the invention
La figure 1 montre une aube 10 d’hélice et en particulier de soufflante d’une turbomachine d’aéronef. Cette aube 10 comprend une pale 12 en composite à matrice organique et un bouclier métallique 14 collé sur un bord d’attaque. La pale 12 comporte en outre un bord de fuite 16, opposé au bord d’attaque, et un intrados et un extrados s’étendant entre les bords d’attaque et de fuite de la pale. FIG. 1 shows a blade 10 of a propeller and in particular of a fan of an aircraft turbomachine. This blade 10 comprises a blade 12 made of organic matrix composite and a metal shield 14 bonded to a leading edge. The blade 12 further comprises a trailing edge 16, opposite the leading edge, and an underside and an upper surface extending between the leading and trailing edges of the blade.
L’aube présente un axe d’allongement noté A qui est un axe radial par rapport à l’axe longitudinal B de la turbomachine dans laquelle est montée cette aube (figure 3). Une extrémité longitudinale de la pale 12 est libre et l’extrémité longitudinale opposée est reliée à un pied 18 pour la fixation de l’aube à un rotor de la turbomachine. The blade has an axis of elongation denoted A which is a radial axis with respect to the longitudinal axis B of the turbomachine in which this blade is mounted (figure 3). A longitudinal end of the blade 12 is free and the opposite longitudinal end is connected to a foot 18 for fixing the blade to a rotor of the turbomachine.
Comme cela est visible à la figure 2, le bouclier 14 comporte deux ailes latérales 14a et 14b s’étendant respectivement sur l’extrados et l’intrados de la pale 12, et un nez 14c reliant les deux ailes 14a et 14b. As can be seen in FIG. 2, the shield 14 comprises two side wings 14a and 14b extending respectively over the upper surface and the lower surface of the blade 12, and a nose 14c connecting the two wings 14a and 14b.
Les ailes 14a, 14b définissent entre elles une cavité de réception du bord d’attaque de la pale 12, ainsi que de colle de solidarisation du bouclier à la pale. The wings 14a, 14b define between them a cavity for receiving the leading edge of the blade 12, as well as glue for securing the shield to the blade.
L’aube 10 peut être fabriquée par un procédé comprenant les étapes de : a) tissage de fibres en trois dimensions de façon à obtenir une préforme fibreuse, b) montage de la préforme dans un moule et injection de résine dans ce moule, de façon à obtenir une pale 12 comportant un extrados et un intrados s’étendant entre un bord d’attaque et un bord de fuite, et c) fixation du bouclier 14 sur le bord de la pale. The blade 10 can be manufactured by a method comprising the steps of: a) weaving fibers in three dimensions so as to obtain a fibrous preform, b) mounting the preform in a mold and injecting resin into this mold, so to obtain a blade 12 comprising an upper surface and a lower surface extending between a leading edge and a trailing edge, and c) fixing the shield 14 on the edge of the blade.
En variante, l’aube 10 pourrait être fabriquée par empilement de nappes ou tissus de fibres, qui sont préalablement ou ensuite imprégnés avec une résine. Plusieurs variantes sont envisageables dans la mesure où le matériau composite de la pale comprend des fibres noyées dans une résine. As a variant, the blade 10 could be manufactured by stacking layers or fabrics of fibers, which are previously or subsequently impregnated with a resin. Several variants are possible insofar as the composite material of the blade comprises fibers embedded in a resin.
Les aubes 10 peuvent être montées sur un disque de rotor 22 pour réaliser une roue de rotor ou un rotor de soufflante, comme cela est visible à la figure 3. Dans le cas d’un module de soufflante, le disque de rotor 22 comprend des aubes 10 à sa périphérie et peut être fixé à un cône 24. The blades 10 can be mounted on a rotor disk 22 to form a rotor wheel or a fan rotor, as can be seen in FIG. 3. In the case of a fan module, the rotor disk 22 comprises vanes 10 at its periphery and can be attached to a cone 24.
L’organigramme de la figure 4 illustre des étapes d’assemblage d’un module de soufflante, selon la technique antérieure. Pour l’essentiel, ce procédé comprend trois étapes à savoir : a) la fabrication des aubes telle qu’évoquée ci-dessus avec la fixation d’un bouclier, par exemple par collage, sur le bord d’une pale, b) le montage des aubes sur le disque de rotor, puis enfin i) l’équilibrage du module en évaluant son balourd et en le corrigeant par des masselottes de poids prédéterminés, rapportées et fixées dans des endroits précis du module (par exemple sur le cône 24). The flowchart in Figure 4 illustrates steps for assembling a fan module, according to the prior art. Essentially, this process comprises three steps, namely: a) the manufacture of the blades as mentioned above with the fixing of a shield, for example by gluing, on the edge of a blade, b) the assembly of the blades on the rotor disc, then finally i) the balancing of the module by evaluating its unbalance and correcting it by weights of predetermined weights, reported and fixed in precise places of the module (for example on the cone 24) .
L’organigramme de la figure 5 illustre des étapes d’assemblage d’un module, par exemple, de soufflante, selon l’invention. Comme on peut le constater, la dernière étape i) du procédé de la figure 4 est supprimée puisqu’il n’y normalement plus besoin d’équilibrage du module postérieurement au montage des aubes sur le disque. Cela est rendu possible grâce à l’équilibrage individuel de chaque aube, par l’ajustement de leur poids moment radial, c’est- à-dire de leur poids moment par rapport à l’axe radial vis-à-vis de l’axe de rotation de l’aube ou du module. The flowchart in FIG. 5 illustrates steps for assembling a module, for example a fan, according to the invention. As can be seen, the last step i) of the process of FIG. 4 is eliminated since there is normally no longer any need to balance the module after mounting the blades on the disc. This is made possible thanks to the individual balancing of each blade, by adjusting their radial moment weight, i.e. their moment weight in relation to the radial axis with respect to the blade or module rotation axis.
Pour l’essentiel, le procédé de la figure 5 comprend, en plus des étapes a) et b) précitées, les étapes de : c) et d), collage du bouclier sur le bord de la pale, ce bouclier étant positionné sur le bord de la pale et dimensionné en fonction du poids moment radial de l’aube, cette étape étant répétée pour chacune des aubes du module, e) et montage des aubes sur le disque de rotor. Avantageusement, et comme illustré aux figures 6a à 6d, le bouclier fixé à l’étape c) comprend au moins un surdimensionnement (L2-L1 ) de façon à pouvoir ajuster le poids moment radial de l’aube en fonction de la position longitudinale du bouclier sur le bord. Ce surdimensionnement est quantifié en fonction de l’équilibrage à réaliser et peut avoir par exemple une masse équivalente de 15g. Essentially, the method of FIG. 5 comprises, in addition to the aforementioned steps a) and b), the steps of: c) and d), bonding the shield to the edge of the blade, this shield being positioned on the edge of the blade and dimensioned according to the radial moment weight of the blade, this step being repeated for each of the blades of the module, e) and assembly of the blades on the rotor disk. Advantageously, and as illustrated in Figures 6a to 6d, the shield fixed in step c) comprises at least one oversizing (L2-L1) so as to be able to adjust the radial moment weight of the blade as a function of the longitudinal position of the shield on the edge. This oversizing is quantified as a function of the balancing to be carried out and may for example have an equivalent mass of 15g.
Ce surdimensionnement (L2-L1) est de préférence réalisé le long de l’axe longitudinal A ou radial de l’aube et est donc une surlongueur, comme illustré dans les dessins. Une surlongueur représentant une masse de 15g, peut par exemple représenter une surlongueur de 1 ,5cm le long de l’axe A dans un cas particulier de réalisation. This oversizing (L2-L1) is preferably made along the longitudinal axis A or radial of the blade and is therefore an overlength, as shown in the drawings. An overlength representing a mass of 15g, can for example represent an overlength of 1.5cm along the axis A in a particular embodiment.
Lors de l’ajustement de la position du bouclier sur le bord, on peut comprendre que cette surlongueur se traduira par un dépassement du bouclier au-delà de l’extrémité supérieure ou radialement externe de la pale (figure 6a - en haut à gauche sur la figure), ou au-delà de l’extrémité inférieure ou radialement interne de la pale (figure 6c - en bas à droite sur la figure), voire même les deux si la pale est par exemple centrée vis-à-vis du bouclier. When adjusting the position of the shield on the edge, it can be understood that this excess length will result in the shield protruding beyond the upper or radially outer end of the blade (figure 6a - top left on the figure), or beyond the lower or radially inner end of the blade (figure 6c - bottom right in the figure), or even both if the blade is for example centered vis-à-vis the shield .
La surlongueur est quantifiée de façon à ce qu’elle autorise des déplacements suffisants du bouclier sur la pale pour ajuster le poids moment radial de l’aube, et de telle sorte que, pour chacune de ces positions, le bord d’attaque de la pale soit recouvert et protégé par le bouclier. On comprend donc que cette surlongueur sera quantifiée en fonction du déplacement maximal envisageable du bouclier sur le bord, pour ajuster le poids moment radial de l’aube. The excess length is quantified so that it allows sufficient movement of the shield on the blade to adjust the radial moment weight of the blade, and so that, for each of these positions, the leading edge of the blade blade is covered and protected by the shield. It is therefore understood that this excess length will be quantified according to the maximum possible displacement of the shield on the edge, to adjust the radial moment weight of the blade.
Dans le cas de la figure 6a, le poids moment radial de l’aube a une valeur minimale. Dans le cas de la figure 6c, le poids moment radial de l’aube a une valeur maximale. In the case of figure 6a, the radial moment weight of the blade has a minimum value. In the case of figure 6c, the radial moment weight of the blade has a maximum value.
L’étape d) qui suit l’étape c) de positionnement et de collage du bouclier 14 consiste à supprimer le surplus, ici longitudinal, du bouclier qui ne doit pas en général dépasser du bord de la pale 12. Dans le cas illustré à la figure 6b, le surplus S1 situé à l’extrémité radialement externe de l’aube est supprimé. Dans le cas illustré à la figure 6d, le surplus S1 situé à l’extrémité radialement interne de l’aube est supprimé. Cette suppression peut être réalisée par usinage. Step d) which follows step c) of positioning and gluing the shield 14 consists in removing the surplus, here longitudinal, of the shield which must not in general exceed the edge of the blade 12. In the case illustrated in FIG. 6b, the excess S1 located at the radially outer end of the blade is eliminated. In the case illustrated in FIG. 6d, the surplus S1 located at the end radially internal vane is removed. This removal can be achieved by machining.
Avant le collage d’un bouclier sur une pale, il peut être utile d’étudier au préalable, lors d’une étape o), l’impact de la position du bouclier sur le bord de la pale, sur le poids moment radial de l’aube. Before bonding a shield to a blade, it may be useful to study beforehand, during a step o), the impact of the position of the shield on the edge of the blade, on the radial moment weight of dawn.
L’invention propose ainsi d’ajuster le poids moment radial des aubes avant l’assemblage d’un module de turbomachine, qui ne nécessite donc pas forcément d’équilibrage propre. The invention thus proposes to adjust the radial moment weight of the blades before assembling a turbomachine module, which therefore does not necessarily require proper balancing.

Claims

REVENDICATIONS
1. Procédé de fabrication d’une aube (10) en matériau composite pour une turbomachine, en particulier d’aéronef, comprenant les étapes de : a) et b) préparation d’une pale à base de fibres noyées dans une résine, la pale comportant un extrados et un intrados s’étendant entre un bord d’attaque et un bord de fuite, c) fixation d’un bouclier de renfort (14) sur un bord de la pale, ce bouclier ayant une forme générale allongée le long d’un axe d’allongement (A) de la pale, caractérisé en ce que le bouclier (14) fixé à l’étape c) comprend au moins un surdimensionnement (L2-L1 ) de façon à pouvoir ajuster le poids moment de l’aube le long dudit axe (A) en fonction de la position du bouclier sur le bord le long de cet axe, et en ce que le procédé comprend une étape suivante d) de suppression d’un surplus (S1 , S2) du bouclier. 1. Method for manufacturing a blade (10) made of composite material for a turbomachine, in particular an aircraft, comprising the steps of: a) and b) preparing a blade based on fibers embedded in a resin, the blade comprising an upper surface and a lower surface extending between a leading edge and a trailing edge, c) fixing a reinforcing shield (14) on one edge of the blade, this shield having a generally elongated shape along of an axis of elongation (A) of the blade, characterized in that the shield (14) fixed in step c) comprises at least one oversizing (L2-L1) so as to be able to adjust the weight moment of the dawn along said axis (A) as a function of the position of the shield on the edge along this axis, and in that the method comprises a following step d) of removing a surplus (S1, S2) from the shield .
2. Procédé selon la revendication 1 , dans lequel les étapes a) et b) comprennent respectivement le : a) tissage de fibres en trois dimensions de façon à obtenir une préforme fibreuse, et le b) montage de la préforme dans un moule et injection de résine dans ce moule, de façon à obtenir une pale (12). 2. Method according to claim 1, in which steps a) and b) respectively comprise: a) weaving fibers in three dimensions so as to obtain a fibrous preform, and b) mounting the preform in a mold and injecting of resin in this mold, so as to obtain a blade (12).
3. Procédé selon la revendication 1 , dans lequel les étapes a) et b) comprennent l’empilement de nappes ou tissus de fibres, qui sont préalablement ou ensuite imprégnés avec une résine. 3. Method according to claim 1, wherein steps a) and b) comprise the stacking of sheets or fabrics of fibers, which are previously or subsequently impregnated with a resin.
4. Procédé selon l’une des revendications précédentes, dans lequel ledit surdimensionnement (L2-L1 ) est une surlongueur du bouclier. 4. Method according to one of the preceding claims, wherein said oversizing (L2-L1) is an overlength of the shield.
5. Procédé selon l’une des revendications précédentes, dans lequel ledit surplus (S1 , S2) est un surplus longitudinal du bouclier (14). 5. Method according to one of the preceding claims, wherein said surplus (S1, S2) is a longitudinal surplus of the shield (14).
6. Procédé selon la revendication 4, dans lequel le surplus (S1 , S2) est situé à une extrémité inférieure ou radialement interne de la pale, ou à une extrémité supérieure ou radialement externe de la pale. 6. Method according to claim 4, in which the surplus (S1, S2) is located at a lower or radially inner end of the blade, or at an upper or radially outer end of the blade.
7. Procédé selon l’une des revendications précédentes, dans lequel il comprend une étape o) préalable d’étude de l’impact de la position du bouclier (14) sur le bord de la pale (12), le long dudit axe (A), sur le poids moment de l’aube (10) le long de cet axe. 7. Method according to one of the preceding claims, in which it comprises a prior step o) of studying the impact of the position of the shield (14) on the edge of the blade (12), along said axis (A), on the moment weight of the blade (10) along this axis.
8. Procédé selon l’une des revendications précédentes, dans lequel ledit surplus (S1 , S2) est supprimé par usinage du bouclier (14). 8. Method according to one of the preceding claims, wherein said surplus (S1, S2) is removed by machining the shield (14).
9. Procédé d’assemblage d’un module de turbomachine, tel qu’un module de soufflante, comprenant une étape de e) montage de plusieurs aubes (10) sur un disque de rotor (22), chacune des aubes étant fabriquée par un procédé selon l’une des revendications précédentes. 9. A method of assembling a turbine engine module, such as a fan module, comprising a step of e) mounting several blades (10) on a rotor disk (22), each of the blades being manufactured by a method according to one of the preceding claims.
PCT/FR2022/051176 2021-06-21 2022-06-16 Method for manufacturing a composite blade for a turbine engine, the blade comprising a reinforcing shield for balancing the blade WO2022269174A1 (en)

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EP22744251.4A EP4359649A1 (en) 2021-06-21 2022-06-16 Method for manufacturing a composite blade for a turbine engine, the blade comprising a reinforcing shield for balancing the blade
CN202280049936.6A CN117716114A (en) 2021-06-21 2022-06-16 Method for manufacturing a composite vane for a turbine engine, the vane comprising a reinforced shroud for balancing the vane

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FR2106574A FR3124217B1 (en) 2021-06-21 2021-06-21 METHOD FOR MANUFACTURING A COMPOSITE TURBOMACHINE BLADE WITH MOMENT WEIGHT CONTROL
FRFR2106574 2021-06-21

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Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2037082A1 (en) 2007-09-13 2009-03-18 Snecma Damping device for a composite blade
CA2999360A1 (en) 2015-09-28 2017-04-06 Safran Aircraft Engines Blade comprising a leading edge shield and method of manufacturing the blade
CA3009226A1 (en) 2015-12-21 2017-06-29 Safran Aircraft Engines Leading edge shield
FR3046557A1 (en) 2016-01-08 2017-07-14 Snecma METHOD FOR MANUFACTURING AN ATTACK EDGE SHIELD COMPRISING AN ADDITIVE MANUFACTURING STEP AND AN ATTACK EDGE SHIELD

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2037082A1 (en) 2007-09-13 2009-03-18 Snecma Damping device for a composite blade
CA2999360A1 (en) 2015-09-28 2017-04-06 Safran Aircraft Engines Blade comprising a leading edge shield and method of manufacturing the blade
CA3009226A1 (en) 2015-12-21 2017-06-29 Safran Aircraft Engines Leading edge shield
FR3046557A1 (en) 2016-01-08 2017-07-14 Snecma METHOD FOR MANUFACTURING AN ATTACK EDGE SHIELD COMPRISING AN ADDITIVE MANUFACTURING STEP AND AN ATTACK EDGE SHIELD

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FR3124217A1 (en) 2022-12-23
EP4359649A1 (en) 2024-05-01
FR3124217B1 (en) 2023-06-30

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